Aeroplane-wing construction



Oct. 1, 1929. OAKS 1,729,680

AEROPLANE WING CONSTRUCTION Filed July 15. 1927 2 Sheets-Sheet l Al'ber f Oaks Oct. 1, 1929. A. oAKs 1,729,680

AEROPLANE WING CONSTRUCTION Filed July 15, 1927 2.Sheets-Shee1 2 gwuwnto'a Alberf 0a #5 Gem "a;

Patented i, 1929 STATES ALBERT OAKS, E CLEVELAND, OHIO AEROPLANE-WING CONSTRUCTION Application filed July 13,

lhis invention relates to new and useful improvements in aeroplane wings, and aims to provide means whereby the spread of the wings may be readily: increased or .di-

minished. y

In carrying out the present invention, there is provided a relatively short length main wing section, being equipped at its opposite ends with secondary sections, which secondary sections may be readily moved inwardly and outwardly of the main wing section for decreasing or increasing the spread of the wing. By reason of an invention of this character, the length of the wing may be slowly diminished while the aeroplane is in flight, thus offering less wind resistance which will materially add to the speed of the plane.

Furthermore, an aeroplane equipped with such a wing structure may fly for a much greater distance than aeroplanes now in use, by reason of the fact that when the length of the wing is reduced, increased speed at less fuel consumption is the result.

The inventionfurther aims to provide a wing of this character, that is no heavier than the lengthy wings now in this use, this feature being present by reason of the fact that obviously,a large number of parts are omitted by reason of the short length of the main wing section, which is the only section that is braced or in any manner connected with the aeroplane fuselage.

In further carrying out my invention, simple but eficient means is provided for permitting the outer secondary sections of the wings to be moved in an inner or outer direction, the means being operable at a point adjacent the aviators seating compartment.

In the drawings Figure 1 is a top plan view of a wing constructed in accordance with the present invention, the same being shown as actually associated with an aeroplane.

Fig. 2 is a front end elevation of the aeroplane equipped with my wing. a

Fig. 3 is a detail transverse section thru the wing, at one end thereof, for disclosing the sliding connections between the main and secondary wing sections.

1927. Serial No. 205,468.

Fig. 4 is a top plan view of one end of the main wing section constructed in accordance with the present invention, the adjacent secondary wing section being slightly spaced therefrom.

Fig. 5 is a detail transverse section thru one of the guide strips for the outer sliding section, and

Fig. 6 is a perspective of one of the cross bars attached to the inner end and under side of each secondary wing section, and cooperating with elements of the main wing section to cause the movement of the secondary sections in reverse directions, and this in a true longitudinal plane with respect to the main wing section.

Now having particular reference to the drawings, there is disclosed an aeroplane wing consisting of .a center main section 5, and a pair of secondary end sections 6-6. In carrying out my invention, the center main section 5 is of much shorter length than the length of the wings now in use on aeroplanes.

However, I do not desire to be limited to any particular length of this central main wing section. At the forward edge of this section 5, the'same is of increased thickness to provide a flange 7 at the top surface of the wing, this flange being undercut to provide a channel extending completely throughout the length of the forward edge of said section 5. Furthermore, the forward edge of the main wing section 5 is beveled to reduce air re sistance.

Arranged longitudinally upon the top side of the main wing section 5 intermediate the lon itudinal ed es thereof is a shaft 8 suitably journaled at its opposite ends within bearings 9 arranged upon the section 5, se. Fig. 4, and the dotted lines in Fig. 1.

Also arranged longitudinally upon the top side of this wing 5 adjacent the outer edges thereof are metallic angle strips 99, the vertically projecting walls of which converge outwardly as clearly disclosed in Fig. 3, and in a detailed sectional view, Fig. 5.

Arranged upon the inner ends of the outer secondary wing sections 66, and at the bot-- tom sides thereof, are transversely extending flat bars 1010 formed in slight spaced relation with their outer ends, and at their centers with widened portions 11 and 12 respectively.

Extending transversely through the central widened portion 12 of each bar 10 is a threaded bore 13 for receiving the shaft 8, which shaft is threaded thruout its length, the threads of one side of the center, extending in one direction, while those of the opposite side of the center, extendin in a reverse direction, so that when the shaft is rotated in one direction, the sections 66 will be moved outwardly, and vice versa.

Intermediate the ends of the shaft '8, the same is equipped with a bevel gear 14, that has mesh with a bevel gear 15, upon the forward end of a rearwardly and downwardly extending shaft 17 that passes through an opening in the center win'g section 5, the opposite end thereof terminating adjacent the cockpit of the areoplane fuselage A and being equipped at this end with a turning wheel 18 As more clearly disclosed in Fig. 3, the forward edges of the sections 66 are beveled for engagement within the channel formed in the flange 7 at the forward edge of the center main section 5. At this point, it ma be well to state that the bar 10-10 on the cut sections 66 are arranged fiushwith the bottom sides of said sections, the bottom sides of the enlarged portions 1111 at the ends of each bar, being provided with transverse slots 1111 that register with slots in ribs 19-19 formed upon the bottom of each end section 6 which slots converge outwardly for receiving the wheel 8 in reverse directions, the end sections 6 are moved inwardly or outwardly with respect to the main sections 5 for thus reducing or increasing the spread of the wing.

Even though I have herein shown and described the invention as consisting of certain detail elements, it is nevertheless to be understood that some changes may be had therefrom without afiecting the spirit and scope of the appended claims.

Having thus described my invention, what I claim as new is ,1. In an aeroplane wing construction of the character described, a central main section, a pair of secondary end sections adapted for longitudinally slidable association with the said main section, overlapping construction maaeeo at the forward longitudinal edge of the central section for engagement over the forward longitudinal edges of the end sections, the re spective end sections each being formed with longitudinally extending and spaced channels, said channels being of outwardly inclined position in cross section, and a pair of spaced upstanding ribs on the central main sections, said ribs being inclined outwardly in vertical disposition and adapted for engagement in the channels of the mairnsections to prevent lateral or vertical displacement of the end sections. 7

2. In an aeroplane wing structure of the characetr described, a central main section, a pair of secondary endsections adapted for longitudinal slidable association with the said mainsection, the respective end sections each being iormed with longitudinally extending and spaced channels, said channels being of outwardly inclined position in cross section, and a pair of spaced upstanding ribs on the central main section, said ribs being inclined outwardly in vertical disposition and adapted for engagement in the channels of the end sections to prevent lateral and vertical displacement o1 the said end sections.

In testimony whereof ll afix my signature.

ALBERT OAKS. 

